CN102007035A

CN102007035A - Composite aircraft joint

Info

Publication number: CN102007035A
Application number: CN2009801101702A
Authority: CN
Inventors: 约翰·弗勒德; 保罗·哈德利; 阿兰·奎尔
Original assignee: Airbus Operations Ltd
Current assignee: Airbus Operations Ltd
Priority date: 2008-03-25
Filing date: 2009-03-12
Publication date: 2011-04-06
Anticipated expiration: 2029-03-12
Also published as: EP2268539A2; CA2719174A1; CN103770932B; RU2010141486A; WO2009118548A2; CN102007035B; GB0805268D0; US20100308170A1; JP5519628B2; KR20110014975A; WO2009118548A3; EP2268539B1; US9308982B2; BRPI0909003A2; CN103770932A; JP2011515278A

Abstract

The present invention relates to a joint between a laminar composite cover and a second cover (which may or may not be also formed from a composite material). The invention also relates to a method of manufacturing such a joint and a method of manufacturing a composite cover suitable for use in such a joint. The laminar composite cover comprises a stack of layers, substantially all of the layers being shaped to form a joggle, each joggle comprising a first portion, a second portion where the layer extends substantially parallel with the first portion, and a ramp between the first and second portions where the layer extends at an angle to the first and second portions, the number of layers being substantially the same on both sides of the ramp. The second cover partially overlaps with the composite cover, and a clamp or fastener holds the covers together where they overlap. The covers have external sides which are substantially aligned with each other so as to form a smooth aerodynamic surface.

Description

The composite aircraft joint

Technical field

The present invention relates to a kind of carry-on joint that is positioned between compound cover of stratiform and second cover (also can make or can't help composite material and make) by composite material.The invention still further relates to a kind of method of making this joint and make the method that is suitable for the compound cover that in this joint, uses.

Background technology

Aircraft component (comprising the part as wing cover and other covers and so on) more and more uses composite material to make, for example laminated product.Be known that utilization is fixed on the wing cover along the fish plate of the joint location between leading edge cover and trailing edge cover and wing cover leading edge cover and the trailing edge cover with wing.These fish plates are fixed on cover on the appropriate location and leading edge and the trailing edge guaranteeing to cover are correctly aimed at the corresponding trailing edge and the leading edge of wing cover.

Usually, use the metal fish plate 1 that in Fig. 1, illustrates and in WO 2007/071905, describe with the cross section.This fish plate be attached at wing cover usually in the wing in-to-in on molded lines (IML) face.The fish plate 1 of prior art has the z type profile of stage portion shape, and its short-and-medium vertical component 1 is connected with two horizontal plate portions 1b, 1c.In this example, plate 1b is assemblied on the part of IML face of aircraft wing covering 2, makes the leading edge of covering 2 dock with vertical component 1a.In place by bolt 3 connections, this bolt 3 sinks in the covering 2 on outer molded lines (OML) face of covering 2.

Dull and stereotyped 1c is attached to the structure of the leading edge of waiting to be fixed to cover.For example the skins front edges 4 of D type outstanding (D-nose) is depicted as and is attached to wing cover leading edge 5 (Fig. 2).In order to reduce the erosion of air-flow 6 for composite skin 2, the covering 4 that this D type is outstanding is selected to have outside the leading edge 5 that enough thickness protrudes in covering 2 usually.Yet, find that the thickness that pneumatic erosion and increase still can take place also can increase resistance.When adopt composite material often regular meeting aggravate pneumatic erosion.

The fish plate of prior art is when hitting bird or similarly clashing into or damageable.Fig. 3 has schematically shown and occurred in by the bump on the attached leading edge structure (not shown) of fish plate 1 is how to cause on the bolt 3 calamitous application force of effect.The present invention seeks to improve at least a part of described problem.

Summary of the invention

A first aspect of the present invention provides a kind of aircraft joint, this joint comprises: the compound cover that comprises the stratiform of a lamination, basically all these layers all are shaped as the formation joggling part, each joggling part comprises first, second portion and the slope between this first and this second portion, state layer in this second portion place and be roughly parallel to this first's extension, state layer in this place, slope and extend with this first and this second portion angledly, the number of plies of these both sides, slope is roughly the same; Second cover, this second cover is overlapped with described compound cover; And anchor clamps or fastener, described anchor clamps or described fastener keep together these covers in the overlapping part of described cover, thus wherein these covers have the lateral surface that forms level and smooth aerodynamic surface roughly aligned with each other.

Another aspect of the present invention provides the method for the aircraft joint of a kind of manufacturing between the composite material cover and second cover, described method comprises: the compound cover that the stratiform that comprises a lamination is provided, basically all layers all are configured as the formation joggling part, each joggling part comprises first, second portion and the slope between this first and this second portion, state layer in this second portion place and be roughly parallel to this first's extension, state layer in this place, slope and extend with this first and this second portion angledly, the number of plies of these both sides, slope is roughly the same; One second cover is overlapped with described compound cover; Utilize anchor clamps or fastener these covers to be kept together in the overlapping part of described cover; And thereby the lateral surface that makes these covers is roughly aligned with each other forms level and smooth aerodynamic surface.

Typically, in the arranged outside guard member of composite material cover, this guard member covers at least a portion on slope.This guard member can be made by composite material, rubber or other any suitable material.

Typically, this guard member has conical in shape, and this conical in shape is thicker relatively towards the bottom on described slope, and is thinner relatively towards the top on described slope.

Described second cover can comprise the leading edge cover or the trailing edge cover of Flight Vehicle Structure, described Flight Vehicle Structure such as wing, tailplane, vertical tail or as the control surface of aileron or wing flap.In this case, described compound cover is typically as the last covering or time covering of the primary element of wing box that extends from second opposite sense that covers on beam and so on.

Alternatively, second cover can comprise manhole cover.In this case, described compound cover is typically as the following covering of wing.

Described guard member can be covered at these and be installed after overlapping, perhaps more preferably, installs before these covers are overlapping.

Described guard member can by adhesive linkage, by common solidify with one of them cover, combination by said method or come attached by other any proper methods.

Preferably, described guard member was pre-formed into conical in shape before being installed to the position that covers the slope.

Preferably, each slope is not to extend in 1/5 angle suddenly with respect to first and second covers.For example each slope is being that 1/8 or 1/10 angle is extended with respect to first and second covers.

One side more of the present invention provides a kind of method of making compound cover, and this method comprises: a guard member is pre-formed into conical in shape; This guard member is installed on the mould; On the described guard member on this mould, lay a folded composite layer, make at least one described layer form the slope whereby; And described folded composite layer is solidified.Typically, make described each layer in folded all be formed with the slope, typically hood-shapedly become Z-shaped or the warpage shape described.

Description of drawings

The specific embodiment of the present invention is described with reference to the accompanying drawings, wherein:

Fig. 1 to Fig. 3 shows the structure of fish plate of the prior art;

Fig. 4 is the block diagram of aircraft wing front-axle beam;

Fig. 5 is the side cross-sectional, view of the joint between wing cover and leading edge panel of wing in Fig. 4;

Fig. 6 shows the method for the wing cover in the constructional drawing 4;

Fig. 7 shows the downside of the wing cover of making according to method shown in Figure 6;

Fig. 8 is the lateral plan of the alternative joint between wing cover and leading edge panel;

Fig. 9 is the lateral plan of rubber edges guard member self; With

Figure 10 is the cutaway view of the warpage joint between wing cover and manhole cover.

The specific embodiment

Fig. 4 shows the front-axle beam of aircraft wing.Described beam comprises web 10, upper flange 11 and lower flange (not shown).Described beam has rounded portion 10a at web 10 and flange 11 intersections.Thereby stratiform composite skin 12 is attached to upper flange 11 and extends the coboundary (the keystone configuration element of wing) that forms wing box to the rear portion of beam.Described as shown in Figure 4, outside the front portion of the outstanding equally slightly described beam of covering 12.

Covering 12 has lateral surface 13 and medial surface as shown in Figure 7 14 as shown in Figure 4.

The detailed structure of covering 12 in manufacturing process has been shown among Fig. 6.Covering 12 is formed by following series of steps:

Edge-protected 22 is the tapered gradually wedge shape in edge from thick relatively end towards relative thin by pre-shape.Can or be impregnated with epoxy resin and the carbon fiber of extrusion molding forms in advance by unidirectionally extruded composite material, rubber for edge-protected 22.In the preferred case, described edge-protected forms in advance by crumpling process, wherein makes carbon fiber and epoxy resin combination, and is spurred by having the mould of expectation cross sectional shape by roller.Make epoxy resin cure or partly solidified thereby heat this mould, make edge-protected 22 to keep self shape

On the profile 28 that is formed with stage portion 29, lay copper film 20

As shown edge-protected 22 is placed on the copper film 20, edge-protected 22 thick end contacts with the stage portion in the copper film.Edge-protected 22 inclined-plane 23 assembled a bonding film FM300 (not shown) before or after it is routed on the mould

First " prepreg " layer 24 is placed on the mould, is attached to described bonding film." prepreg " layer 24 comprises the carbon fiber of the individual event arrangement that is impregnated with epoxy resin-matrix

One folded " prepreg " layer material is laid on the mould, changes on demand and cross this folded machine direction, go up final layer 25 (it will form the inside face of covering 12) up to laying

The vacuum bag (not shown) is laid on the final layer 25 optional and other combination of elements such as antiadhesion barrier of this vacuum bag

Space between vacuum bag and the mould is evacuated in autoclave, makes prepreg and edge-protected 22 complete curing thereby this autoclave is heated to solidification temperature above epoxy resin simultaneously

Remove vacuum bag etc., remaining curing covering 12 as shown in Figure 7.

Be stacked in the profile that edge-protected 22 top formed the Z-shaped what is called " joggling part " that has the slope.Each layer in folded all is shaped as the formation joggling part, each joggling part includes the slope between first, second portion and first and the second portion, at described second portion place, described layer is roughly parallel to first and extends, at place, described slope, described layer extends with first and second portion angledly.For example, second horizontal component 47 that Die one of them interior layer is included in first horizontal component 45 " top " (in this example with respect to the orientation shown in Fig. 5 definition top and the bottom) on slope 46 located and 46 " bottom " located on the slope.

Notice that the slope extends through folded thick entirely, thereby exterior layer 24 and interior layer 25 are formed with

slope

26,27 respectively with all interior layers.The lateral surface 13 of covering is owing to engage with mould in solidification process, so its shape (is called " outer molded lines " or OML) is able to accuracy control.

Notice that the number of plies in folding is identical in the both sides on slope.Thus, there is not the discontinuous layer that can cause the porosity problem in Die inside.

At Liang Shanghou, the most clear overlapped joint that illustrates is engaged to leading edge panel 15 with it in the section drawing by Fig. 5 in covering 12 Bolt Connection.Described panel 15 can by or can't help similar composite material and make.

As shown in Figure 5, the lateral surface 13 of the medial surface of panel 15 and covering 12 is overlapped.The lateral surface of edge-protected 22 and panel 15 and the lateral surface of covering 12 be common form be exposed to shown in the roughly continuous pneumatic outside face of air-flow.Then, make fastener (as bolt) pass covering 12 and panel 15 overlaid parts along line 31.For the purpose of checking or repairing, thereby can be removed can be so that joint be separated this fastener.

Described edge-protected 22 between the trailing edge 30 of slope and panel 15, and protection is avoided the granule that air-flow (advancing along direction shown in Fig. 5) carries and is corroded at the edge 32 at the downstream top place on slope 26.Aviation weighting material (not shown) is inserted in space between the trailing edge 30 of edge-protected 22 and panel 15 when general assembly.

In the inboard of cover 12, " top " 33 on slope is positioned to be positioned as close to beam 11, thereby the rounded portion 10a of slope and beam is overlapped (in this example with respect to definition top of the orientation shown in Fig. 5 and bottom).This makes edge 34 phase places of cover 12 become relatively near beam.

Fig. 8 and 9 shows edge-protected alternate forms.Identical among the majority element of this structure and Fig. 5, and components identical adopts identical Reference numeral.In this example, make and form sealing member between covering 12 and panel 15 by preform rubber for edge-protected.Described edge-protected has bevelled wedge-like portion 40 that covers the slope and the afterbody 41 that forms sealing member between lap, show described afterbody the most clearly in Fig. 9.In this example edge-protected can be overlapping and be attached on panel 15 or the covering 12 by the adhesive linkage (not shown) before forming joint at panel 15 and covering 12.Also show rib 42 among Fig. 8, covering 12 and panel 15 by Bolt Connection to rib 42.

Preferably, described rubber edges guard member is attached on the panel 15 in advance, rather than is attached to covering 12.This has formed and has been damaged or removable part when wearing and tearing, and to not influence of main structure.

Figure 10 shows the warpage joint between stratiform composite skin 50 and manhole cover 54.Bottom covering that described composite skin 50 is aircraft wing and surperficial within it going up are carried a series of T type stringers, there is shown the part of one of them this stringer 52 in the cross section.

Manhole cover 54 is pressed on the covering 50 by pressing plate 53.Described manhole cover 54 and pressing plate 53 all are approximate ellipsoidals when seeing below aircraft wing.Covering 50 is formed with oval opening to receive pressing plate 53.Described pressing plate 53 has the annular lip 55 that engages with the inside face of covering 50.Rubber seal liner 56 shown in the dotted line provides the sealing member of fuel proof between flange 55 and covering 50.

Manhole cover 54 engages with pressing plate 53 along its periphery by series of fasteners 57.Fastener 57 is clamped in covering 50 between two

parts

53 and 54 when fastened.Rubber gasket 58 shown in dotted line provides the sealing member of fuel proof between manhole cover 54 and covering 50.Bevelled weighting material 59 is provided between liner 58 and covering 50.

Covering 50 is to be formed with the warpage lamination with the covering 12 similar modes shown in Fig. 6.Pressing plate 53 and fastener 57 are used as anchor clamps together, thereby hold them in together in the overlapping part of part 50,54.Thereby fastener 57 can be removed and make joint to be opened and provide and enter wing in-to-in inlet.Covering 50 and manhole cover 54 have lateral surface roughly aligned with each other, thereby form level and smooth aerodynamic surface.

Wherein leading edge panel 15 has the aforementioned embodiments formation contrast of constant thickness, and the thickness of manhole cover 54 is tapered towards narrow relatively edge 60, and tapering is according to the angle on the slope in the joggling part 61.The lateral surface of covering 50 is formed with the annular recess with stage portion 61, and described stage portion is held liner 58, thereby liner 58 is flushed with the lateral surface of covering 50 and the lateral surface of manhole cover 54.

Liner 58 and taper weighting material 59 are protected the edge 60 of manhole cover 54 and the short grained erosion that covering 50 is avoided carrying in the air-flow together as edge-protected.

Although the present invention is illustrated with reference to one or more preferred implementations, what it should be understood that is can make various conversion or improvement under the situation of the invention scope that does not exceed the claims protection.

Claims

1. aircraft joint, this joint comprises: the compound cover that comprises the stratiform of a lamination, basically all these layers all are shaped as the formation joggling part, each joggling part comprises first, second portion and the slope between this first and this second portion, state layer in this second portion place and be roughly parallel to this first's extension, state layer in this place, slope and extend with this first and this second portion angledly, the number of plies of these both sides, slope is roughly the same; Second cover, this second cover is partly overlapping with described compound cover; And anchor clamps or fastener, described anchor clamps or described fastener keep together these covers in the overlapping part of described cover, thus wherein these covers have the lateral surface that forms level and smooth aerodynamic surface roughly aligned with each other.

2. joint as claimed in claim 1, this joint also are included in the guard member on the described lateral surface of described compound cover, and this guard member covers at least a portion on described slope.

3. joint as claimed in claim 2, wherein said guard member is formed by composite material.

4. as claim 2 or 3 described joints, wherein said guard member has conical in shape, and this conical in shape is thicker relatively towards the bottom on described slope, and is thinner relatively towards the top on described slope.

5. the described joint of arbitrary as described above claim, wherein said second cover comprises the leading edge cover or the trailing edge cover of aircraft wing.

6. the described joint of arbitrary as described above claim, the top on wherein said slope is positioned at the rear of the bottom on this slope.

7. the overlapping part that the described joint of arbitrary as described above claim, wherein said anchor clamps or fastener are included in described cover is passed the fastener of these covers.

8. the described joint of arbitrary as described above claim, wherein each slope is not to extend in 1/5 angle suddenly with respect to described first cover and described second cover.

9. Flight Vehicle Structure, this Flight Vehicle Structure comprises: beam; Be attached to the compound cover of the stratiform on the described beam; Second cover; And between layered compound cover and described second the cover between according to the described joint of aforementioned arbitrary claim.

10. the method for the manufacturing aircraft joint between the compound cover and second cover, described method comprises: the compound cover that the stratiform that comprises a lamination is provided, basically all layers all are configured as the formation joggling part, each joggling part comprises first, second portion and the slope between this first and this second portion, state layer in this second portion place and be roughly parallel to this first's extension, state layer in this place, slope and extend with this first and this second portion angledly, the number of plies of these both sides, slope is roughly the same; Make one second cover partly overlapping with described compound cover; Utilize anchor clamps or fastener these covers to be kept together in the overlapping part of described cover; And thereby the lateral surface that makes these covers is roughly aligned with each other forms level and smooth aerodynamic surface.

11. also being included in, method as claimed in claim 10, this method make described cover a guard member is attached to one of them described cover before overlapping.

12. method as claimed in claim 11, this method also are included in described guard member is attached to before the described cover, this guard member is pre-formed into conical in shape.

13., described guard member and described compound cover are solidified jointly as claim 11 or 12 described methods.

14. as each described method in the claim 11 to 13, this method also comprises by with material pulling and/or be pressed through mould with expectation cross sectional shape and the described guard member of preform.

15. a method of making compound cover, this method comprises: a guard member is pre-formed into conical in shape; This guard member is installed on the mould; On the described guard member on this mould, lay a folded composite layer, make at least one described layer form the slope whereby; And described folded composite layer is solidified.

16. method as claimed in claim 15 wherein makes described guard member and described folded composite layer solidify jointly.

17. as claim 15 or 16 described methods, this method makes this guard member partly solidified at least before also being included in and being installed to described guard member on the described mould.

18. as each described method in the claim 15 to 17, wherein by with material pulling and/or be pressed through mould and the described guard member of preform with expectation cross sectional shape.

19. as each described method in the claim 15 to 17, described layer that wherein will be all basically all is configured as the formation joggling part, each joggling part comprises first, second portion and the slope between this first and this second portion, state layer in this second portion place and be roughly parallel to this first's extension, state layer in this place, slope and extend with this first and this second portion angledly, the number of plies of these both sides, slope is roughly the same.